WO2000071880B1 - Systeme de propulsion simplifie a haut rendement - Google Patents

Systeme de propulsion simplifie a haut rendement

Info

Publication number
WO2000071880B1
WO2000071880B1 PCT/US2000/012658 US0012658W WO0071880B1 WO 2000071880 B1 WO2000071880 B1 WO 2000071880B1 US 0012658 W US0012658 W US 0012658W WO 0071880 B1 WO0071880 B1 WO 0071880B1
Authority
WO
WIPO (PCT)
Prior art keywords
oxidizer
propulsion system
fuel
rocket propulsion
liquid
Prior art date
Application number
PCT/US2000/012658
Other languages
English (en)
Other versions
WO2000071880A3 (fr
WO2000071880A2 (fr
Inventor
James A Bowery
Roger E Gregory
Original Assignee
James A Bowery
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by James A Bowery filed Critical James A Bowery
Priority to AU67467/00A priority Critical patent/AU6746700A/en
Priority to EP00955238A priority patent/EP1185778A2/fr
Publication of WO2000071880A2 publication Critical patent/WO2000071880A2/fr
Publication of WO2000071880A3 publication Critical patent/WO2000071880A3/fr
Publication of WO2000071880B1 publication Critical patent/WO2000071880B1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/46—Feeding propellants using pumps
    • F02K9/48—Feeding propellants using pumps driven by a gas turbine fed by propellant combustion gases or fed by vaporized propellants or other gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/46—Feeding propellants using pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/62—Combustion or thrust chambers
    • F02K9/66—Combustion or thrust chambers of the rotary type

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)

Abstract

Cette invention concerne un moteur de fusée simplifié qui comprend un assemblage rotor dans lequel une pompe à liquides à ultracentrifugation (avec une vitesse tangentielle au-dessus de 200 m/s) est disposée autour d'une chambre de combustion pour assurer le refroidissement forcé par convection à effet de Coriolis de ladite chambre de combustion et, à la fois, le refroidissement libre régénératif par convection aidé par l'accélération centripète et pour comprimer en même temps le propergol liquide. Le carburant et le comburant peuvent être stockés à des températures cryogéniques et pompés autour de la chambre de combustion à des fins de refroidissement régénératif. La chambre de combustion peut être construite pour pivoter de concert avec la pompe afin d'assurer la combustion améliorée grâce à l'effet de Coriolis et l'accélération centripète. L'ensemble rotor est entraîné directement par un composant tangentiel du vecteur de poussée primaire au moyen de buses inclinées ou grâce à des ailettes, des cannelures ou autres surfaces de réaction. On peut utiliser comme propergol et comme agent de refroidissement de l'oxygène liquide et du propane liquide, maintenus à une température et à une pression à peu près égales et stockés dans un réservoir en polyéthylène téréphtalate ou autre matière polymère.
PCT/US2000/012658 1999-05-14 2000-05-08 Systeme de propulsion simplifie a haut rendement WO2000071880A2 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
AU67467/00A AU6746700A (en) 1999-05-14 2000-05-08 Simplified high-efficiency propulsion system
EP00955238A EP1185778A2 (fr) 1999-05-14 2000-05-08 Systeme de propulsion simplifie a haut rendement

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US09/312,585 1999-05-14
US09/312,585 US6212876B1 (en) 1999-05-14 1999-05-14 Simplified high-efficiency propulsion system

Publications (3)

Publication Number Publication Date
WO2000071880A2 WO2000071880A2 (fr) 2000-11-30
WO2000071880A3 WO2000071880A3 (fr) 2001-01-18
WO2000071880B1 true WO2000071880B1 (fr) 2001-03-01

Family

ID=23212136

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2000/012658 WO2000071880A2 (fr) 1999-05-14 2000-05-08 Systeme de propulsion simplifie a haut rendement

Country Status (5)

Country Link
US (1) US6212876B1 (fr)
EP (1) EP1185778A2 (fr)
AU (1) AU6746700A (fr)
TW (1) TW479107B (fr)
WO (1) WO2000071880A2 (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU2001297846A1 (en) * 2000-11-20 2002-12-23 Cryoco, Inc. A method and apparatus for the preparation and usage of a cryogenic propellant or explosive system
WO2003087564A1 (fr) * 2002-04-11 2003-10-23 Haase Richard A Procedes, processus, systemes et appareils de la technologie de combustion de l'eau pour la combustion d'hydrogene et d'oxygene
KR20040023396A (ko) * 2002-09-11 2004-03-18 현대모비스 주식회사 스월 혼합기 설계방법
US6807805B2 (en) * 2003-03-11 2004-10-26 United Technologies Corporation Hypergolic fuel system
US20110017874A1 (en) * 2007-11-26 2011-01-27 Clearvalue Technologies, Inc. Means of fuel and oxidizer storage
US9650997B2 (en) 2013-03-05 2017-05-16 John Bossard Rotary turbo rocket
RU2554126C1 (ru) * 2013-12-18 2015-06-27 Федеральное государственное унитарное предприятие "Государственный космический научно-производственный центр имени М.В. Хруничева" Объединенная двигательная установка ракетного блока
UA108043C2 (en) * 2013-12-30 2015-03-10 Oleksandr Illarionovych Yudin Continuous-flow rotary heater
CN114412663B (zh) * 2021-12-23 2023-08-29 北京航天动力研究所 一种一体化液体火箭发动机推力室顶盖结构

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2519878A (en) * 1946-07-31 1950-08-22 Carold F Bjork Rocket projectile
US2516462A (en) * 1946-10-17 1950-07-25 Daniel And Florence Guggenheim Double jacket means for feeding two liquids to a rotating combustion chamber
US2523011A (en) * 1947-11-01 1950-09-19 Daniel And Florence Guggenheim Cooling and feeding means for rotating combustion chambers
US2536599A (en) * 1948-01-02 1951-01-02 Daniel And Florence Guggenheim Steam-operated rotating combustion chamber
US3553964A (en) * 1968-01-15 1971-01-12 Thiokol Chemical Corp Propellant feed system for rocket powerplants

Also Published As

Publication number Publication date
TW479107B (en) 2002-03-11
WO2000071880A3 (fr) 2001-01-18
AU6746700A (en) 2000-12-12
EP1185778A2 (fr) 2002-03-13
US6212876B1 (en) 2001-04-10
WO2000071880A2 (fr) 2000-11-30

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